US20080166235A1 - Wind Turbine Airfoil Family - Google Patents
Wind Turbine Airfoil Family Download PDFInfo
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- US20080166235A1 US20080166235A1 US11/621,272 US62127207A US2008166235A1 US 20080166235 A1 US20080166235 A1 US 20080166235A1 US 62127207 A US62127207 A US 62127207A US 2008166235 A1 US2008166235 A1 US 2008166235A1
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- airfoils
- airfoil
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- 238000000926 separation method Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000001010 compromised effect Effects 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor
- F03D1/06—Rotors
- F03D1/0608—Rotors characterised by their aerodynamic shape
- F03D1/0633—Rotors characterised by their aerodynamic shape of the blades
- F03D1/0641—Rotors characterised by their aerodynamic shape of the blades of the section profile of the blades, i.e. aerofoil profile
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2240/00—Components
- F05B2240/20—Rotors
- F05B2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05B2240/301—Cross-section characteristics
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S416/00—Fluid reaction surfaces, i.e. impellers
- Y10S416/02—Formulas of curves
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S416/00—Fluid reaction surfaces, i.e. impellers
- Y10S416/05—Variable camber or chord length
Definitions
- the present application relates generally to wind turbines and more particularly relates to a family of airfoil configurations for an inboard region of a wind turbine blade.
- Conventional wind turbines generally include two or more turbine blades or vanes connected to a central hub. Each blade extends from the hub at a root of the blade and continues to a tip. A cross-section of the blade is defined as an airfoil.
- the shape of an airfoil may be defined in relationship to a chord line. The chord line is a measure or line connecting the leading edge of the airfoil with the trailing edge of the airfoil.
- the shape may be defined in the form of X and Y coordinates from the chord line.
- the X and Y coordinates generally are dimensionless.
- the thickness of an airfoil refers to the distance between the upper surface and the lower surface of the airfoil and is expressed as a fraction of the chord length.
- the inboard region i.e., the area closest to the hub, generally requires the use of relatively thick foils (30% ⁇ t/c ⁇ 40%).
- the aerodynamic performance of conventional airfoil designs degrades rapidly for thicknesses greater than 30% of chord largely due to flow separation concerns. For thicknesses above 40% of chord, massive flow separation may be unavoidable such that the region of the blade may be aerodynamically compromised.
- Each airfoil may include a blunt trailing edge, a substantially oval shaped suction edge, and a substantially S-shaped pressure side.
- the airfoils may include a chord line extending from a leading edge to the blunt trailing edge.
- the substantially oval shaped suction sides and the substantially S-shaped pressure sides do not intersect the chord line.
- the suction sides may include non-dimensional coordinate values of X and positive Y set forth in Tables 1-4.
- the pressure sides may include non-dimensional coordinate values of X and negative Y set forth in Tables 1-4.
- Each of airfoils is connected by a smooth curve.
- Each airfoil may include a first width about the blunt trailing edge, a second width moving towards a leading edge, with the second width being smaller than the first width, and a third width moving further towards the leading edge, with the third width being larger than the first width.
- Each airfoil may include a curved leading edge.
- a first airfoil may include a profile substantially in accordance with non-dimensional coordinate values of X and Y set forth in Table 1.
- a second airfoil may include a profile substantially in accordance with non-dimensional coordinate values of X and Y set forth in Table 2.
- a third airfoil may include a profile substantially in accordance with non-dimensional coordinate values of X and Y set forth in Table 3.
- a fourth airfoil may include a profile substantially in accordance with non-dimensional coordinate values of X and Y set forth in Table 4.
- Each airfoil may be an inboard region airfoil.
- the present application further describes a turbine blade having a number of airfoils.
- the airfoils may include a first airfoil with a profile substantially in accordance with non-dimensional coordinate values of X and Y set forth in Table 1, a second airfoil with a profile substantially in accordance with non-dimensional coordinate values of X and Y set forth in Table 2, a third airfoil with a profile substantially in accordance with non-dimensional coordinate values of X and Y set forth in Table 3, and a fourth airfoil with a profile substantially in accordance with non-dimensional coordinate values of X and Y set forth in Table 4.
- the airfoils are connected by a smooth curve.
- the X and Y values may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil.
- the airfoils may include a number of inboard region airfoils.
- the turbine blade may be a wind turbine blade.
- FIG. 1 is a perspective view of a blade as is described herein with a number of airfoils shown.
- FIG. 2 is a composite plot of the airfoils as are described herein.
- FIG. 1 shows a blade 100 as is described herein.
- the blade 100 includes the inboard region 110 adjacent to the hub (not shown), an outboard region 120 or the middle portion, and a tip region 130 .
- the inboard region 110 generally takes up about the first half of the blade 100 or so, the outboard region generally takes up about the next forty percent (40%) or so, and the tip 130 takes up about the final ten percent (10%) or so of the blade 100 .
- the figures may vary.
- FIG. 2 shows a family of airfoils 140 .
- the airfoils 140 are designed for the inboard region 110 of the blade 100 .
- four (4) airfoils 140 are shown, a first airfoil 150 , a second airfoil 160 , a third airfoil 170 , and a fourth airfoil 180 .
- An infinite number of the airfoils 140 may be used.
- a chord line 190 extends from, a leading edge 200 to a trailing edge 210 of each of the airfoils 140 .
- the chord line 190 extends through the middle of the airfoils 140 .
- each airfoil 140 also includes a suction side 220 and a pressure side 230 .
- Each suction side 220 has a substantially oval shape while each pressure side 230 has a substantially S-shape.
- the suction sides 220 and the pressure sides 230 do not intersect the chord line 190 .
- Each of the airfoils 140 is connected by a smooth curve.
- the specific shape of the airfoil 150 is given in Table 1 in the form of dimensionless coordinates.
- the X/C values represent locations on the chord line 190 in relation to the trailing edge 210 .
- the Y/C values represent heights from the chord line 190 to point on either the suction side 220 or the pressure side 230 .
- the values are scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil.
- the shape of the second airfoil 160 is defined as follows:
- the shape of the third airfoil 170 is similar to those described above, but again thicker.
- the shape of the third airfoil 170 is defined as follows:
- the shape of the fourth airfoil 180 is similar to that as described above, but again thicker.
- the shape of the fourth airfoil 180 is defined as follows:
- the extent of the pressure recovery on the airfoil suction surface is alleviated. Such permits the flow to remain attached so as to provide substantial lift performance. Specifically, lift coefficients greater than 3.0 have been measured.
- the airfoils 140 thus provide improved aerodynamic performance and efficiency with improved structural stiffness (bending moment of inertia). These improvements lead to increase energy capture and reduce blade weight. Indirectly, the airfoils 140 also minimize the aerodynamic compromise due to transportation constraints (max chord). The dip between the 1.0 and the 0.8 positions also reduces the overall weight as compared to known blunt trailing edge designs.
Abstract
Description
- The present application relates generally to wind turbines and more particularly relates to a family of airfoil configurations for an inboard region of a wind turbine blade.
- Conventional wind turbines generally include two or more turbine blades or vanes connected to a central hub. Each blade extends from the hub at a root of the blade and continues to a tip. A cross-section of the blade is defined as an airfoil. The shape of an airfoil may be defined in relationship to a chord line. The chord line is a measure or line connecting the leading edge of the airfoil with the trailing edge of the airfoil. The shape may be defined in the form of X and Y coordinates from the chord line. The X and Y coordinates generally are dimensionless. Likewise, the thickness of an airfoil refers to the distance between the upper surface and the lower surface of the airfoil and is expressed as a fraction of the chord length.
- The inboard region, i.e., the area closest to the hub, generally requires the use of relatively thick foils (30%≦t/c≦40%). The aerodynamic performance of conventional airfoil designs, however, degrades rapidly for thicknesses greater than 30% of chord largely due to flow separation concerns. For thicknesses above 40% of chord, massive flow separation may be unavoidable such that the region of the blade may be aerodynamically compromised.
- Thus, there is a need for an airfoil design that provides improved aerodynamic performance particularly with respect to the inboard region. Preferably, such a design would provide improved aerodynamic performance and efficiency while providing improved structural stiffness and integrity.
- The present application thus provides a family of airfoils for a wind turbine blade. Each airfoil may include a blunt trailing edge, a substantially oval shaped suction edge, and a substantially S-shaped pressure side.
- The airfoils may include a chord line extending from a leading edge to the blunt trailing edge. The substantially oval shaped suction sides and the substantially S-shaped pressure sides do not intersect the chord line. The suction sides may include non-dimensional coordinate values of X and positive Y set forth in Tables 1-4. The pressure sides may include non-dimensional coordinate values of X and negative Y set forth in Tables 1-4. Each of airfoils is connected by a smooth curve.
- Each airfoil may include a first width about the blunt trailing edge, a second width moving towards a leading edge, with the second width being smaller than the first width, and a third width moving further towards the leading edge, with the third width being larger than the first width. Each airfoil may include a curved leading edge.
- A first airfoil may include a profile substantially in accordance with non-dimensional coordinate values of X and Y set forth in Table 1. A second airfoil may include a profile substantially in accordance with non-dimensional coordinate values of X and Y set forth in Table 2. A third airfoil may include a profile substantially in accordance with non-dimensional coordinate values of X and Y set forth in Table 3. A fourth airfoil may include a profile substantially in accordance with non-dimensional coordinate values of X and Y set forth in Table 4. Each airfoil may be an inboard region airfoil.
- The present application further describes a turbine blade having a number of airfoils. The airfoils may include a first airfoil with a profile substantially in accordance with non-dimensional coordinate values of X and Y set forth in Table 1, a second airfoil with a profile substantially in accordance with non-dimensional coordinate values of X and Y set forth in Table 2, a third airfoil with a profile substantially in accordance with non-dimensional coordinate values of X and Y set forth in Table 3, and a fourth airfoil with a profile substantially in accordance with non-dimensional coordinate values of X and Y set forth in Table 4. The airfoils are connected by a smooth curve.
- The X and Y values may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil. The airfoils may include a number of inboard region airfoils. The turbine blade may be a wind turbine blade.
- These and other features of the present application will become apparent to one of ordinary skill in the art upon review of the following detailed description when taken in conjunction with the several drawing and the appended claims.
-
FIG. 1 is a perspective view of a blade as is described herein with a number of airfoils shown. -
FIG. 2 is a composite plot of the airfoils as are described herein. - Referring now to the drawings, in which like numerals refer to like elements throughout the several views,
FIG. 1 shows ablade 100 as is described herein. Theblade 100 includes theinboard region 110 adjacent to the hub (not shown), anoutboard region 120 or the middle portion, and atip region 130. Theinboard region 110 generally takes up about the first half of theblade 100 or so, the outboard region generally takes up about the next forty percent (40%) or so, and thetip 130 takes up about the final ten percent (10%) or so of theblade 100. The figures may vary. -
FIG. 2 shows a family ofairfoils 140. Theairfoils 140 are designed for theinboard region 110 of theblade 100. In this example, four (4)airfoils 140 are shown, afirst airfoil 150, asecond airfoil 160, athird airfoil 170, and afourth airfoil 180. An infinite number of theairfoils 140 may be used. Achord line 190 extends from, a leadingedge 200 to atrailing edge 210 of each of theairfoils 140. In this example, thechord line 190 extends through the middle of theairfoils 140. - In this example, the
trailing edges 210 are blunt or have a “flat back”. The leadingedges 200 are curved. Eachairfoil 140 also includes asuction side 220 and apressure side 230. Eachsuction side 220 has a substantially oval shape while eachpressure side 230 has a substantially S-shape. Thesuction sides 220 and thepressure sides 230 do not intersect thechord line 190. Each of theairfoils 140 is connected by a smooth curve. - The specific shape of the
airfoil 150 is given in Table 1 in the form of dimensionless coordinates. The X/C values represent locations on thechord line 190 in relation to thetrailing edge 210. The Y/C values represent heights from thechord line 190 to point on either thesuction side 220 or thepressure side 230. The values are scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil. -
TABLE 1 x/c y/c 1.00000000 0.03726164 0.90036720 0.06785235 0.80067860 0.08990651 0.70007530 0.10734770 0.60106600 0.12091980 0.50066880 0.13214710 0.40005820 0.14126440 0.30031070 0.14733190 0.20042560 0.14654610 0.10049920 0.12712570 0.00000000 0.00000000 0.10065920 −0.12659800 0.20022940 −0.14866100 0.30009620 −0.15000300 0.40096110 −0.13401000 0.50042920 −0.10618000 0.60041830 −0.07248480 0.70074310 −0.03982390 0.80018960 −0.01648170 0.90094460 −0.01118480 1.00000000 −0.03773510 - As is shown at the X=1 location, the
trailing edge 210 of theairfoil 140 has a given width. That width narrows towards the X=0.9 position, continues to narrow and then expands until past the X=0.3 position. The shape again narrows towards the leadingedge 200 in a largely oval shape and then returns towards thetrading edge 210. - The
second airfoil 160 is similar but somewhat thicker. As above, thesecond airfoil 160 also has the narrowing dip between the position X=1 and the position X=0.8. The shape of thesecond airfoil 160 is defined as follows: -
TABLE 2 x/c y/c 1.00000000 0.07476157 0.90046010 0.10220790 0.80029790 0.12248030 0.70049780 0.13862410 0.60022080 0.15149490 0.50073840 0.16167160 0.40103380 0.16936190 0.30001950 0.17332270 0.20017300 0.16904810 0.10033560 0.14399980 0.00000000 0.00000000 0.10085420 −0.14364800 0.20034960 −0.17120100 0.30024750 −0.17597900 0.40050510 −0.16227900 0.50051480 −0.13568000 0.60100430 −0.10275700 0.70074630 −0.07116550 0.80063010 −0.04891650 0.90051680 −0.04553450 1.00000000 −0.07523460 - The shape of the
third airfoil 170 is similar to those described above, but again thicker. Thethird airfoil 170 also has the dip between the position X=1 and the position X=0.8. The shape of thethird airfoil 170 is defined as follows: -
TABLE 3 x/c y/c 1.00000000 0.11226081 0.90063769 0.13652491 0.80109208 0.15473962 0.70100077 0.16967702 0.60050336 0.18158922 0.50083265 0.19073012 0.40094014 0.19697082 0.30087793 0.19867672 0.20005762 0.19089852 0.10048941 0.16042992 0.00000000 0.00000000 0.10034881 −0.15978302 0.20060802 −0.19312702 0.30043493 −0.20132002 0.40002894 −0.18996502 0.50060705 −0.16471402 0.60057116 −0.13303101 0.70081557 −0.10227001 0.80004708 −0.08139181 0.90013649 −0.07984641 0.90125599 −0.07998141 1.00000000 −0.11273501 - The shape of the
fourth airfoil 180 is similar to that as described above, but again thicker. Thefourth airfoil 180 has the dip between the position X=1 and the position X=0.8. The shape of thefourth airfoil 180 is defined as follows: -
TABLE 4 x/c y/c 1.00000000 0.13726020 0.90000000 0.15989241 0.80000000 0.17787950 0.70000000 0.19334258 0.60000000 0.20609266 0.50000000 0.21607175 0.40000000 0.22261591 0.30000000 0.22363103 0.20000000 0.21369481 0.10000000 0.17827485 0.00000000 0.00002100 0.10000000 −0.17758316 0.20000000 −0.21583323 0.30000000 −0.22630101 0.40000000 −0.21557439 0.50000000 −0.19017060 0.60000000 −0.15766700 0.70000000 −0.12602585 0.80000000 −0.10435340 0.90000000 −0.10306262 1.00000000 −0.13773604 - By incorporating a relatively
thick trailing edge 210, the extent of the pressure recovery on the airfoil suction surface is alleviated. Such permits the flow to remain attached so as to provide substantial lift performance. Specifically, lift coefficients greater than 3.0 have been measured. Theairfoils 140 thus provide improved aerodynamic performance and efficiency with improved structural stiffness (bending moment of inertia). These improvements lead to increase energy capture and reduce blade weight. Indirectly, theairfoils 140 also minimize the aerodynamic compromise due to transportation constraints (max chord). The dip between the 1.0 and the 0.8 positions also reduces the overall weight as compared to known blunt trailing edge designs. - It should be apparent that the foregoing relates only to the preferred embodiments of the present application and that numerous changes and modifications may be made herein by one of ordinary skill in the art without departing from the general spirit and scope of the invention as defined by the following claims and the equivalents thereof.
Claims (18)
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
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US11/621,272 US7883324B2 (en) | 2007-01-09 | 2007-01-09 | Wind turbine airfoil family |
DK200701853A DK200701853A (en) | 2007-01-09 | 2007-12-21 | Family of wind turbine carriers |
DE102008003411.8A DE102008003411B4 (en) | 2007-01-09 | 2008-01-08 | Wind turbine airfoil family |
CN200810001367XA CN101230836B (en) | 2007-01-09 | 2008-01-09 | Wind turbine airfoil family |
US13/022,347 US8226368B2 (en) | 2007-01-09 | 2011-02-07 | Wind turbine airfoil family |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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US11/621,272 US7883324B2 (en) | 2007-01-09 | 2007-01-09 | Wind turbine airfoil family |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US13/022,347 Continuation-In-Part US8226368B2 (en) | 2007-01-09 | 2011-02-07 | Wind turbine airfoil family |
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US20080166235A1 true US20080166235A1 (en) | 2008-07-10 |
US7883324B2 US7883324B2 (en) | 2011-02-08 |
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US11/621,272 Active 2029-12-10 US7883324B2 (en) | 2007-01-09 | 2007-01-09 | Wind turbine airfoil family |
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US (1) | US7883324B2 (en) |
CN (1) | CN101230836B (en) |
DE (1) | DE102008003411B4 (en) |
DK (1) | DK200701853A (en) |
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US20110189024A1 (en) * | 2007-01-09 | 2011-08-04 | General Electric Company | Wind Turbine Airfoil Family |
US8226368B2 (en) | 2007-01-09 | 2012-07-24 | General Electric Company | Wind turbine airfoil family |
US20100143152A1 (en) * | 2009-06-30 | 2010-06-10 | Balaji Subramanian | Method and apparatus for increasing lift on wind turbine blade |
US8011886B2 (en) | 2009-06-30 | 2011-09-06 | General Electric Company | Method and apparatus for increasing lift on wind turbine blade |
US9790795B2 (en) | 2010-10-22 | 2017-10-17 | Mitsubishi Heavy Industries, Ltd. | Wind turbine blade, wind power generation system including the same, and method for designing wind turbine blade |
US8047784B2 (en) | 2011-03-22 | 2011-11-01 | General Electric Company | Lift device for rotor blade in wind turbine |
US8403642B2 (en) | 2011-09-27 | 2013-03-26 | General Electric Company | Wind turbine rotor blade assembly with root curtain |
US8430633B2 (en) | 2011-11-21 | 2013-04-30 | General Electric Company | Blade extension for rotor blade in wind turbine |
US8376703B2 (en) | 2011-11-21 | 2013-02-19 | General Electric Company | Blade extension for rotor blade in wind turbine |
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US10578078B2 (en) | 2012-02-09 | 2020-03-03 | General Electric Company | Wind turbine rotor blade assembly with root extension panel and method of assembly |
EP2959161B1 (en) | 2013-02-19 | 2019-04-17 | Senvion GmbH | Rotor blade of a wind turbine |
US9523279B2 (en) | 2013-11-12 | 2016-12-20 | General Electric Company | Rotor blade fence for a wind turbine |
CN105840414A (en) * | 2016-03-22 | 2016-08-10 | 西北工业大学 | Airfoil family suitable for 5-10 mw wind turbine blades |
Also Published As
Publication number | Publication date |
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US7883324B2 (en) | 2011-02-08 |
CN101230836A (en) | 2008-07-30 |
DE102008003411A1 (en) | 2008-07-10 |
DE102008003411B4 (en) | 2021-09-02 |
CN101230836B (en) | 2013-02-06 |
DK200701853A (en) | 2008-07-10 |
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